EP3580443B1 - Turbogebläse mit zwischenströmung zur luftzufuhr über radialarme zu einem abgasgehäuse dieses turbogebläses - Google Patents

Turbogebläse mit zwischenströmung zur luftzufuhr über radialarme zu einem abgasgehäuse dieses turbogebläses Download PDF

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Publication number
EP3580443B1
EP3580443B1 EP18706791.3A EP18706791A EP3580443B1 EP 3580443 B1 EP3580443 B1 EP 3580443B1 EP 18706791 A EP18706791 A EP 18706791A EP 3580443 B1 EP3580443 B1 EP 3580443B1
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EP
European Patent Office
Prior art keywords
casing
pressure compressor
exhaust casing
casings
radial arms
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EP18706791.3A
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English (en)
French (fr)
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EP3580443A1 (de
Inventor
Antoine Jean-Philippe Beaujard
Tewfik BOUDEBIZA
Catherine Pikovsky
Bastien Pierre Verdier
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/608—Aeration, ventilation, dehumidification or moisture removal of closed spaces

Definitions

  • the invention relates to the supply of air to radial arms of an exhaust casing fitted to a turbofan engine.
  • a turbofan engine has an inlet sleeve receiving air which is sucked in by a low pressure compressor and then divided into a central primary flow and a secondary flow surrounding the primary flow.
  • the secondary flow circulates in a space called secondary vein which is delimited externally by a secondary vein casing also called engine hull, and internally by an envelope surrounding the primary flow.
  • the primary flow circulates in a space called the primary vein delimited externally by the envelope and internally by a succession of fixed and rotating internal elements.
  • the fixed internals include rectifier and distributor platforms, and inner casing shrouds, and the rotating internals include rotor bladed wheel platforms.
  • purges blow air from the internal regions towards the primary vein, through each space longitudinally separating a fixed internal element and a rotating internal element. These purges ensure that hot air from the primary vein does not enter colder interior regions.
  • the primary flow circulates between an internal casing and an external casing of a high pressure compressor to be compressed in this high pressure compressor before being burned in a combustion chamber. It is then expanded in a high pressure turbine to drive the high pressure compressor, then into a low pressure turbine to drive the low pressure compressor, before being expelled backwards generating thrust.
  • the envelope externally delimiting the primary vein is thus formed by a series of casings comprising a high pressure compressor casing, a casing at the level of the combustion chamber and a high pressure turbine casing, as well as by an external casing shell. 'exhaust.
  • Each turbine and each compressor is formed of stages each comprising a series of rotating blades regularly spaced around a central longitudinal axis of the engine, possibly preceded by a distributor in the case of a turbine or possibly followed by a rectifier in the case of a compressor.
  • the distributors and rectifiers consist of a series of fixed vanes.
  • the rear part of such an engine comprises, downstream of the low pressure turbine, an exhaust casing, usually designated by the acronym TRF (Turbine Rear Frame), which carries a bearing supporting a rear end of the engine rotor.
  • TRF Transbine Rear Frame
  • This exhaust casing comprises an internal shroud and an external shroud and radial arms securing these shrouds to one another, passing radially through the primary vein.
  • the bearing that the exhaust casing supports is supplied by air coming from the secondary vein being routed by the arms of the exhaust casing. This air is used in particular to cool the radial arms and to externally pressurize a lubrication enclosure in which the bearing carried by this exhaust casing is housed.
  • the casings surrounding the primary vein carry on their external faces elements such as fuel rails, variable pitch blade control systems or others. These elements protrude, so that they introduce significant pressure losses for the portion of the secondary flow which runs alongside them and in which the supply air passing through the radial arms of the exhaust casing is collected.
  • the pressure at the level of the collection openings may prove insufficient to generate sufficient flow in the radial arms of the exhaust casing.
  • One solution could consist of collecting the air by means of a scoop extending radially from the casings surrounding the primary stream, at the level of the radial arms, but such a scoop would introduce turbulence which would be detrimental to the flow of the secondary flow.
  • the aim of the invention is to provide an architecture making it possible to improve the air supply through the radial arms of the exhaust casing.
  • the pressure prevailing at the inlet of the radial feed arms of the casing corresponds to the static pressure increased by the dynamic pressure at the low pressure compressor outlet, without the flow of the secondary flow being disturbed.
  • the invention also relates to a turbojet engine thus defined, in which the sucked air is divided at an intermediate casing located between the low pressure compressor and the high pressure compressor, to form the central primary flow, the intermediate flow, and the secondary flow.
  • the invention also relates to a turbojet engine thus defined, in which the air supplied to the central region of the exhaust casing contributes to pressurizing the joints of a lubrication enclosure in which a bearing carried by this exhaust casing is housed. .
  • the invention also relates to a turbojet engine thus defined, in which the air supplied to the central region of the exhaust casing supplies a purge located upstream of the exhaust casing.
  • the invention also relates to a turbojet thus defined, in which the radial arms of the exhaust casing comprise pierced liners arranged so that the air passing through these radial arms cools the walls of these arms.
  • the invention also relates to a turbojet engine thus defined, in which the inlet opening of the intermediate vein is a circumferential opening surrounding the primary vein.
  • the invention also relates to a turbojet thus defined, in which the fairing joins the external shroud of the exhaust casing downstream of the radial arms of this exhaust casing.
  • the idea underlying the invention is to collect the air intended to pass through the radial arms of the exhaust casing, directly downstream of the low pressure compressor in order to benefit from the static pressure increased by the dynamic pressure downstream. of the low pressure compressor.
  • a dual-flow turbojet engine 1 comprises an inlet sleeve 2 in which the air is sucked in by the blades of a low-pressure compressor 3 surrounded by a casing 4 of the low-pressure compressor, to then be divided into three flows at the level an intermediate casing 5 extending longitudinally between the low pressure compressor and a high pressure compressor. These three flows include a central primary flow 6, an intermediate flow 7 surrounding the primary flow, and a secondary flow 8 which surrounds the intermediate flow 7.
  • the primary flow 6 circulates in a primary vein which is delimited internally by a succession of internal fixed elements and internal rotating elements.
  • the fixed internals include rectifier and distributor platforms, and inner casing shrouds, and the rotating internals include rotor bladed wheel platforms.
  • This primary vein is delimited externally by a series of casings which surround it and which include a high pressure compressor casing 9, a casing surrounding the combustion chamber and a casing surrounding the high pressure turbine jointly identified by 10, as well as by a external shroud of the exhaust casing.
  • the intermediate flow circulates between on the one hand the series of casings delimiting the primary vein, and on the other hand an intermediate fairing 11 which surrounds them over all their lengths.
  • the secondary flow circulates in a secondary vein delimited internally by the intermediate fairing 11 and externally by a secondary vein casing 12 surrounding the intermediate fairing 11.
  • the intermediate casing 5 comprises an outer shell and an inner shell connected by radial arms, and it is located between the low pressure compressor 3 and the high pressure compressor 24. Its outer shell connects the casing 4 of the low pressure compressor to the vein casing secondary 12, and its internal shell and supports the bearings of these compressors.
  • An upstream circular edge 18 of the high pressure compressor outer casing, and an upstream circular edge 19 of the intermediate fairing 11 are located at this intermediate casing 5.
  • the upstream circular edge 18 of the high pressure compressor casing internally delimits an opening of circumferential entrance 23 of the primary vein.
  • the upstream circular edge 19 of the fairing 11 delimits with the edge 18 a circumferential inlet opening 21 of the intermediate vein, and it delimits with the secondary vein casing 12 a circumferential inlet opening 22 of the secondary vein.
  • These inlet openings both have the shape of crowns and they both receive air having undergone low pressure compression and circulating in the intermediate casing 5.
  • edges 18 and 19 can where appropriate be formed directly in the intermediate casing in the form of corresponding nozzles extended respectively by the high pressure compressor casing and by the intermediate fairing 11.
  • the primary flow 6 passes through a high pressure compressor 24 before reaching a combustion chamber 26 to then be expanded in a high pressure turbine 28 then in a low pressure turbine 29.
  • the high pressure turbine 28 comprises a disc 31 carrying corresponding blades, this disc being secured to a high pressure body 25 extending upstream to the compressor 24 of which this high pressure body 25 also carries the blades.
  • the low pressure turbine 29 comprises two discs 32, 33 carrying corresponding blades, and which are secured to a low pressure journal 34 having a downstream end received in a bearing 36.
  • This bearing 36 is located in the central region of a casing. exhaust 38 which surrounds it while ensuring its maintenance.
  • This exhaust casing 38 comprises an internal ferrule and an external ferrule which externally delimits the primary vein, as well as radial arms 39 securing these ferrules to one another.
  • the external shell extends in continuity with the series of casings 9, 10 and the radial arms pass radially through the primary vein, the assembly being located downstream of the low pressure turbine 29.
  • This exhaust casing 38 also carries an outlet cone 41 which is surrounded by a confluence wall 42, downstream of the low pressure turbine 29 and the radial arms 39.
  • This confluence wall which is fixed to a flange of the casing exhaust extends in the extension of the external shell of the exhaust casing to guide the secondary flow so that it presents the most regular flow possible, that is to say without disturbances.
  • One or more of the radial arms 39 is hollow, so as to convey into a central region of this exhaust casing 38 air coming from the intermediate vein to in particular pressurize the joints of the lubrication enclosure of the bearing carried by this casing, along a path F represented in dotted lines on the figures 1 And 2 .
  • the intermediate fairing 11 surrounds the series of casings externally delimiting the primary vein from the intermediate casing corresponding to the outlet of the low pressure compression portion, to the rear of the engine downstream of the radial arms 39.
  • the series of casings 9 and 10 carry on their external face different equipment, such as flanges, fuel rails, variable-pitch blade control systems or others, marked 37.
  • the intermediate fairing 11 begins with the first equipment of the high-pressure compressor.
  • the different pieces of equipment 37 are all located in the intermediate vein instead of being located in the secondary vein, so that they do not introduce any pressure loss in the secondary vein.
  • this fairing 11 surrounds the series of casings 9, 10 to delimit with it an annular space for circulation of the air flow of the intermediate vein.
  • This fairing 11 has a downstream end 43 located after the radial arms 39 which tightens to join the external shroud of the exhaust casing so that the intermediate vein is closed at its rear end.
  • This downstream end 43 has the shape of an annular conduit separating into several conical axial conduits.
  • Each conical conduit ends in an elbow oriented towards a radial arm 39 of the exhaust casing 38 to form a scoop.
  • the entire intermediate flow 7 is thus evacuated through the internal channel(s) of the different radial arms 39 in particular to cool these arms.
  • This air is more particularly intended to pressurize the seals of the lubrication enclosure of the bearing carried by this casing, and to supply a low pressure turbine purge.
  • the pressure which reigns in the entire intermediate vein corresponds to the total pressure at its inlet 21, that is to say to the static pressure of the air which has been compressed by the compressor low pressure 3 increased by dynamic pressure. Indeed, the flow rate of the intermediate flow is relatively low, the pressure losses introduced by the elements 37 are reduced.
  • the pressure prevailing at the inlet of the radial arms 39 is worth the total pressure prevailing at the inlet 21, that is to say the static pressure resulting from the compression delivered by the low pressure compressor increased by dynamic pressure.
  • the invention thus makes it possible, despite the presence of elements 37 protruding from the external face of the series of casings 9, 10, to maintain a sufficiently high pressure of the flow along the external face of this series of casings. It allows more limit the turbulence of the secondary flow which no longer runs along the irregularities constituted by elements 37.
  • the intermediate flow 7 which passes through the radial arms of the exhaust casing, cools these arms, pressurizes the lubrication enclosure enclosing the bearing carried by this exhaust casing, and it also supplies a purge located between the last rotating stage of the low pressure turbine and the exhaust casing.
  • the radial arms 39 are equipped with pierced internal liners arranged to improve thermal convection along the walls of these arms.
  • the flow 7 passes through the arms 39 of the casing to cool them, and a first part of the remaining air is directed towards the environment of the lubrication enclosure carried by the exhaust casing, to contribute to its pressurization, this which is represented by arrow 46.
  • a second part of the remaining air is directed towards the purge 49 located between the last stage of the low pressure turbine and the exhaust casing 38.
  • the purge 49 is supplemented by air 47 coming from upstream of the turbine .
  • the intermediate flow can also be used to cool a high pressure turbine casing in order to reduce the clearance existing between the blade ends of the high pressure turbine and this casing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (6)

  1. Zweistrahliges Turbostrahltriebwerk (1), das Folgendes umfasst:
    - einen Niederdruckkompressor (3);
    - eine Reihe von Gehäusen (9, 10), die sich stromabwärts vom Niederdruckkompressor (3) erstrecken, um einen Primärströmungskanal zum Zirkulieren eines Primärstroms (6) zu begrenzen, und eine stromaufwärts gelegene Kante (18) umfassen, die eine umlaufende Einlassöffnung (23) des Primärstroms (6) begrenzt;
    - einen Hochdruckkompressor (24), der sich im Primärströmungskanal befindet;
    - eine Verkleidung (11), die die Reihe von Gehäusen (9, 10) umgibt, um mit der Reihe von Gehäusen (9, 10) einen Zwischenströmungskanal zum Zirkulieren eines Zwischenstroms (7) zu begrenzen, wobei die Verkleidung eine stromaufwärts gelegene Kante (19) aufweist, die die Reihe von Gehäusen (9, 10) umgibt, um mit der Reihe von Gehäusen (9, 10) eine Einlassöffnung (21) zu begrenzen, die sich stromaufwärts des Hochdruckkompressors (24) befindet;
    - ein Sekundärströmungskanalgehäuse (12), das die Zwischenverkleidung (11) umgibt, um mit der Verkleidung (11) einen Sekundärströmungskanal zum Zirkulieren eines Sekundärstroms (8) zu begrenzen;
    - ein Abgasgehäuse (38), das einen Außenmantel umfasst, der sich in die Erstreckung der Reihe von Gehäusen (9, 10) erstreckt, sowie radiale Arme, die von dem Außenmantel ausgehen, wobei mindestens einer der radialen Arme (39) die vom Zwischenströmungskanal kommende Luft sammelt, um einen zentralen Bereich des Abgasgehäuses (38) mit Druckluft zu versorgen, in dem die durch den Niederdruckkompressor (3) angesaugte Luft auf Höhe eines Zwischengehäuses (5), das sich zwischen dem Niederdruckkompressor (3) und dem Hochdruckkompressor (24) befindet, aufgeteilt wird, um den zentralen Primärstrom (6), den Zwischenstrom (7) und den Sekundärstrom (8) zu bilden.
  2. Turbostrahltriebwerk nach Anspruch 1, bei dem die im zentralen Bereich des Abgasgehäuses (38) bereitgestellte Luft dazu beiträgt, die Dichtungen einer Schmierkammer mit Druck beaufschlagt werden, in der eine vom Abgasgehäuse (38) getragene Lageranordnung untergebracht ist.
  3. Turbostrahltriebwerk nach einem der Ansprüche 1 oder 2, bei dem die im zentralen Bereich des Abgasgehäuses (38) bereitgestellte Luft eine Lüftungsöffnung (49) versorgt, die sich stromaufwärts des Abgasgehäuses (38) befindet.
  4. Turbostrahltriebwerk nach einem der Ansprüche 1 bis 3, bei dem die radialen Arme (39) des Abgasgehäuses (38) durchbrochene Umhüllungen umfassen, die so angeordnet sind, dass die die radialen Arme (39) durchquerende Luft die Wände der Arme kühlt.
  5. Turbostrahltriebwerk nach einem der Ansprüche 1 bis 4, bei dem die Einlassöffnung (21) des Zwischenströmungskanals eine umlaufende Öffnung ist, die den Primärströmungskanal umgibt.
  6. Turbostrahltriebwerk nach einem der Ansprüche 1 bis 5, bei dem sich die Verkleidung (11) stromabwärts der radialen Arme (39) des Abgasgehäuses (38) mit dem Außenmantel des Abgasgehäuses verbindet.
EP18706791.3A 2017-02-07 2018-02-05 Turbogebläse mit zwischenströmung zur luftzufuhr über radialarme zu einem abgasgehäuse dieses turbogebläses Active EP3580443B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1700128A FR3062678B1 (fr) 2017-02-07 2017-02-07 Turboreacteur a double flux comprenant une veine intermediaire dediee a l'alimentation en air par des bras radiaux d'un carter d'echappement de ce turboreacteur
PCT/FR2018/050275 WO2018146405A1 (fr) 2017-02-07 2018-02-05 Turboréacteur a double flux comprenant une veine intermédiaire dédiée a l'alimentation en air par des bras radiaux d'un carter d'échappement de ce turboréacteur

Publications (2)

Publication Number Publication Date
EP3580443A1 EP3580443A1 (de) 2019-12-18
EP3580443B1 true EP3580443B1 (de) 2024-05-15

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EP18706791.3A Active EP3580443B1 (de) 2017-02-07 2018-02-05 Turbogebläse mit zwischenströmung zur luftzufuhr über radialarme zu einem abgasgehäuse dieses turbogebläses

Country Status (5)

Country Link
US (1) US11499439B2 (de)
EP (1) EP3580443B1 (de)
CN (1) CN110268152B (de)
FR (1) FR3062678B1 (de)
WO (1) WO2018146405A1 (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3062681B1 (fr) * 2017-02-07 2020-11-20 Safran Aircraft Engines Turboreacteur a architecture de paliers optimisee pour le support d'un arbre basse pression
FR3088955B1 (fr) 2018-11-27 2020-12-25 Safran Aircraft Engines Turboréacteur à double flux comprenant un cône de sortie refroidi par son flux secondaire
US11391179B2 (en) 2019-02-12 2022-07-19 Pratt & Whitney Canada Corp. Gas turbine engine with bearing support structure
US11346249B2 (en) 2019-03-05 2022-05-31 Pratt & Whitney Canada Corp. Gas turbine engine with feed pipe for bearing housing
US11460037B2 (en) 2019-03-29 2022-10-04 Pratt & Whitney Canada Corp. Bearing housing
FR3101379B1 (fr) * 2019-09-30 2022-08-26 Safran Aircraft Engines Pressurisation d’enceinte de turbomachine avec de l’air provenant de la veine secondaire
FR3108655B1 (fr) * 2020-03-24 2022-07-15 Safran Aircraft Engines Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement

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Publication number Priority date Publication date Assignee Title
GB695482A (en) * 1950-11-28 1953-08-12 Rolls Royce Improvements in or relating to gas-turbine engines
GB938247A (en) * 1962-03-26 1963-10-02 Rolls Royce Gas turbine engine having cooled turbine blading
FR2824598B1 (fr) * 2001-05-10 2003-07-18 Snecma Moteurs Dispositif de ventilation d'une nacelle du corps d'un turboreacteur
US7614210B2 (en) * 2006-02-13 2009-11-10 General Electric Company Double bypass turbofan
US9004849B2 (en) * 2012-01-10 2015-04-14 United Technologies Corporation Gas turbine engine forward bearing compartment architecture
JP6039059B2 (ja) * 2012-05-02 2016-12-07 ゲーコーエヌ エアロスペース スウェーデン アーベー ガスタービンエンジンの支持構造
FR3039207B1 (fr) * 2015-07-21 2019-07-26 Safran Aircraft Engines Carter d'echappement d'une turbomachine a duree de vie augmentee

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Publication number Publication date
WO2018146405A1 (fr) 2018-08-16
CN110268152A (zh) 2019-09-20
FR3062678B1 (fr) 2019-04-19
FR3062678A1 (fr) 2018-08-10
US11499439B2 (en) 2022-11-15
CN110268152B (zh) 2022-11-25
US20200032664A1 (en) 2020-01-30
EP3580443A1 (de) 2019-12-18

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